基于高超声速飞机平台的拦截中制导方法研究  

Research on interception midcourse guidance method based on hypersonic aircraft platform

作　　者：王健权 尹中杰 王雷 乔鸿 刘凯 Wang Jianquan;Yin Zhongjie;Wang Lei;Qiao Hong;Liu Kai(School of Aeronautics and Astronautics,Dalian University of Technology,Dalian 116024,China;Shanghai Institute of Mechanical and Electrical Engineering,Shanghai 201109,China;Beijing Institute of Aerospace Technology,Beijing 100074,China)

机构地区：[1]大连理工大学航空航天学院,大连116024 [2]上海机电工程研究所,上海201109 [3]北京空天技术研究所,北京100074

出　　处：《空天技术》2022年第6期67-76,共10页Aerospace Technology

基　　金：国家自然科学基金(U2141229);航空科学基金(2019ZC063001)。

摘　　要：针对基于吸气式高超声速飞机拦截平台的临近空间高机动目标中制导拦截问题,开展了在线中制导律设计方法研究。考虑到高超声速拦截平台的气动/动力耦合特性与吸气式发动机工作状态约束,设计了一种双层在线中制导律,顶层以前向拦截中末制导交班条件作为末端约束,以比例系数、油门为优化变量,燃料消耗为性能指标,采用高斯伪谱法阶段性在线规划拦截轨迹,底层采用轨迹线性化控制方法实现轨迹剖面跟踪制导。通过仿真分析验证了轨迹设计及制导方法的有效性,并与传统比例导引法进行对比仿真,验证了该中制导方法的优越性。Aiming at the interception midcourse guidance problem of high maneuverable targets in near space based on air-breathing hypersonic aircraft interception platform,the guidance law design method in online interception is studied.Considering the airframe/scramjet integration coupling characteristics and working condition constraints of high intercept platform,a dual level online interception guidance law is presented.At the top level,Gaussian pseudo-spectral method is used to plan the intercept trajectory online in stages.The handover conditions of midcourse and terminal guidance are used as the end constraints,with proportional coefficient and throttle as optimization variables and fuel consumption as performance index.At the bottom level,trajectory linearization control method is used to realize trajectory tracking guidance.The effectiveness of the trajectory design and guidance method is verified by simulation analysis.The superiority of the guidance method is verified by comparing with the traditional proportional guidance method.

关 键 词：高超声速飞机 临近空间目标拦截 双层在线制导律 轨迹线性化控制 高斯伪谱法 

分 类 号：V448.23[航空宇航科学与技术—飞行器设计]